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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.56 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e853-il-1000000.txt
Download as CSV file: xf-e853-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3321   0.09680   0.09534  -0.0420   1.0000   0.0083
 -10.500  -0.3365   0.09149   0.09005  -0.0437   0.9998   0.0085
 -10.250  -0.3357   0.08567   0.08424  -0.0468   0.9990   0.0086
 -10.000  -0.3351   0.07964   0.07821  -0.0503   0.9982   0.0087
  -9.750  -0.3338   0.07369   0.07227  -0.0539   0.9971   0.0089
  -9.500  -0.3371   0.06612   0.06471  -0.0584   0.9960   0.0089
  -9.250  -0.3569   0.05191   0.05050  -0.0663   0.9950   0.0088
  -9.000  -0.3861   0.03801   0.03641  -0.0783   0.9923   0.0085
  -8.750  -0.3995   0.03088   0.02910  -0.0884   0.9862   0.0085
  -8.500  -0.4036   0.02595   0.02394  -0.0961   0.9773   0.0085
  -8.250  -0.3948   0.02141   0.01916  -0.1008   0.9708   0.0088
  -8.000  -0.3853   0.01842   0.01597  -0.1021   0.9598   0.0090
  -7.750  -0.3664   0.01591   0.01327  -0.1039   0.9510   0.0093
  -7.500  -0.3382   0.01312   0.01023  -0.1074   0.9454   0.0098
  -7.250  -0.3554   0.01719   0.01304  -0.1068   0.9460   0.0049
  -7.000  -0.3182   0.01631   0.01204  -0.1093   0.9406   0.0047
  -6.750  -0.2826   0.01345   0.00887  -0.1120   0.9331   0.0044
  -6.500  -0.2465   0.01193   0.00714  -0.1145   0.9221   0.0043
  -6.250  -0.2136   0.01090   0.00591  -0.1160   0.9070   0.0044
  -6.000  -0.1848   0.01020   0.00500  -0.1166   0.8904   0.0044
  -5.750  -0.1580   0.00972   0.00437  -0.1165   0.8742   0.0046
  -5.500  -0.1326   0.00899   0.00342  -0.1163   0.8588   0.0056
  -5.250  -0.1062   0.00870   0.00302  -0.1161   0.8449   0.0077
  -5.000  -0.0800   0.00828   0.00260  -0.1159   0.8323   0.0237
  -4.750  -0.0533   0.00810   0.00239  -0.1159   0.8208   0.0342
  -4.500  -0.0267   0.00785   0.00219  -0.1158   0.8099   0.0554
  -4.250  -0.0001   0.00749   0.00196  -0.1159   0.7997   0.1015
  -4.000   0.0262   0.00699   0.00172  -0.1161   0.7904   0.1840
  -3.750   0.0526   0.00644   0.00149  -0.1164   0.7816   0.2930
  -3.500   0.0796   0.00609   0.00137  -0.1166   0.7734   0.3778
  -3.250   0.1072   0.00602   0.00131  -0.1166   0.7656   0.4144
  -3.000   0.1351   0.00596   0.00126  -0.1167   0.7580   0.4375
  -2.750   0.1630   0.00596   0.00123  -0.1168   0.7513   0.4570
  -2.500   0.1911   0.00593   0.00121  -0.1169   0.7444   0.4761
  -2.250   0.2189   0.00596   0.00118  -0.1169   0.7382   0.4864
  -2.000   0.2472   0.00596   0.00116  -0.1170   0.7319   0.4959
  -1.750   0.2751   0.00598   0.00115  -0.1171   0.7262   0.5064
  -1.500   0.3034   0.00598   0.00116  -0.1172   0.7206   0.5185
  -1.250   0.3315   0.00600   0.00116  -0.1173   0.7150   0.5289
  -1.000   0.3595   0.00603   0.00116  -0.1174   0.7100   0.5376
  -0.750   0.3878   0.00602   0.00117  -0.1175   0.7048   0.5443
  -0.500   0.4159   0.00606   0.00118  -0.1176   0.6998   0.5506
  -0.250   0.4440   0.00608   0.00119  -0.1178   0.6952   0.5565
   0.000   0.4723   0.00608   0.00121  -0.1179   0.6903   0.5628
   0.250   0.5003   0.00612   0.00124  -0.1180   0.6857   0.5690
   0.500   0.5284   0.00614   0.00128  -0.1181   0.6812   0.5755
   0.750   0.5566   0.00616   0.00131  -0.1182   0.6763   0.5823
   1.000   0.5843   0.00620   0.00135  -0.1183   0.6710   0.5894
   1.250   0.6123   0.00621   0.00139  -0.1183   0.6647   0.5969
   1.500   0.6398   0.00625   0.00144  -0.1183   0.6580   0.6049
   1.750   0.6675   0.00626   0.00149  -0.1183   0.6511   0.6132
   2.000   0.6947   0.00632   0.00154  -0.1182   0.6434   0.6225
   2.250   0.7223   0.00632   0.00161  -0.1182   0.6351   0.6321
   2.500   0.7493   0.00637   0.00168  -0.1181   0.6251   0.6424
   2.750   0.7760   0.00643   0.00174  -0.1179   0.6144   0.6538
   3.000   0.8035   0.00645   0.00183  -0.1179   0.6054   0.6662
   3.250   0.8305   0.00650   0.00192  -0.1178   0.5956   0.6795
   3.500   0.8572   0.00656   0.00203  -0.1176   0.5845   0.6944
   3.750   0.8836   0.00662   0.00214  -0.1173   0.5699   0.7105
   4.000   0.9096   0.00671   0.00226  -0.1170   0.5525   0.7282
   4.250   0.9334   0.00692   0.00241  -0.1163   0.5190   0.7480
   4.500   0.9559   0.00721   0.00262  -0.1153   0.4745   0.7705
   4.750   0.9745   0.00780   0.00296  -0.1137   0.4018   0.7961
   5.000   0.9902   0.00859   0.00346  -0.1116   0.3173   0.8269
   5.250   1.0030   0.00946   0.00401  -0.1089   0.2279   0.8697
   5.500   1.0140   0.01001   0.00442  -0.1057   0.1632   1.0000
   5.750   1.0312   0.01082   0.00491  -0.1040   0.1060   1.0000
   6.000   1.0511   0.01142   0.00533  -0.1028   0.0737   1.0000
   6.250   1.0719   0.01193   0.00573  -0.1017   0.0520   1.0000
   6.500   1.0930   0.01241   0.00612  -0.1007   0.0378   1.0000
   6.750   1.1141   0.01286   0.00652  -0.0996   0.0274   1.0000
   7.000   1.1351   0.01331   0.00697  -0.0985   0.0199   1.0000
   7.250   1.1526   0.01400   0.00757  -0.0968   0.0080   1.0000
   7.500   1.1689   0.01477   0.00836  -0.0948   0.0042   1.0000
   7.750   1.1872   0.01535   0.00899  -0.0932   0.0036   1.0000
   8.000   1.2025   0.01602   0.00973  -0.0910   0.0032   1.0000
   8.250   1.2142   0.01686   0.01067  -0.0882   0.0030   1.0000
   8.500   1.2237   0.01785   0.01178  -0.0850   0.0029   1.0000
   8.750   1.2306   0.01902   0.01309  -0.0816   0.0028   1.0000
   9.000   1.2368   0.02031   0.01450  -0.0782   0.0028   1.0000
   9.250   1.2419   0.02180   0.01612  -0.0748   0.0028   1.0000
   9.500   1.2500   0.02317   0.01760  -0.0720   0.0028   1.0000
   9.750   1.2596   0.02450   0.01906  -0.0697   0.0028   1.0000
  10.000   1.2721   0.02551   0.02016  -0.0678   0.0027   1.0000
  10.250   1.2827   0.02680   0.02156  -0.0658   0.0027   1.0000
  10.500   1.2949   0.02783   0.02268  -0.0640   0.0026   1.0000
  10.750   1.3049   0.02916   0.02412  -0.0622   0.0026   1.0000
  11.000   1.3143   0.03053   0.02560  -0.0604   0.0025   1.0000
  11.250   1.3199   0.03253   0.02776  -0.0583   0.0025   1.0000
  11.500   1.3249   0.03457   0.02995  -0.0563   0.0024   1.0000
  11.750   1.3278   0.03687   0.03243  -0.0544   0.0024   1.0000
  12.000   1.3291   0.03934   0.03508  -0.0525   0.0024   1.0000
  12.250   1.3267   0.04229   0.03823  -0.0507   0.0024   1.0000
  12.500   1.3216   0.04559   0.04174  -0.0490   0.0024   1.0000
  12.750   1.3157   0.04895   0.04529  -0.0477   0.0024   1.0000
  13.000   1.3083   0.05258   0.04911  -0.0468   0.0024   1.0000
  13.250   1.2962   0.05696   0.05370  -0.0462   0.0024   1.0000
  13.500   1.2837   0.06157   0.05850  -0.0462   0.0024   1.0000
  13.750   1.2661   0.06718   0.06433  -0.0468   0.0025   1.0000
  14.000   1.2499   0.07294   0.07029  -0.0480   0.0025   1.0000
  14.250   1.2318   0.07941   0.07695  -0.0500   0.0025   1.0000
  14.500   1.2130   0.08650   0.08419  -0.0529   0.0025   1.0000
  14.750   1.1925   0.09458   0.09245  -0.0568   0.0025   1.0000
  15.000   1.1714   0.10353   0.10157  -0.0617   0.0025   1.0000
  15.250   1.1496   0.11356   0.11176  -0.0677   0.0026   1.0000
  15.500   1.1268   0.12500   0.12336  -0.0750   0.0026   1.0000
  15.750   1.1035   0.13785   0.13635  -0.0831   0.0026   1.0000
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